Airfoil shape for a compressor vane

ABSTRACT

An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE A. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances can be joined smoothly with one another to form a complete airfoil shape.

BACKGROUND OF THE INVENTION

The present invention relates to airfoils for a vane of a gas turbine. In particular, the invention relates to compressor airfoil profiles for a Stage 1 stator vane.

In a gas turbine, many system requirements should be met at each stage of a gas turbine's flow path section to meet design goals. A turbine hot gas path requires that the compressor airfoil stator vane meet design goals and desired requirements of efficiency, reliability, and loading. For example, and in no way limiting of the invention, a vane of a compressor stator should achieve thermal and mechanical operating requirements for that particular stage. Further, for example, and in no way limiting of the invention, a vane of a compressor stator should achieve thermal and mechanical operating requirements for that particular stage.

Past efforts to meet design goals and desired requirements have provided coatings on the airfoil, but the coatings may not be robust enough or permanent to provide design goals and desired requirements. Accordingly, it is desirable to provide an airfoil configuration with a profile meet to design goals and desired requirements.

BRIEF DESCRIPTION OF THE INVENTION

In one embodiment of the invention, an article of manufacture comprises a vane airfoil having an airfoil shape, the airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE A. X and Y are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape.

In another embodiment according to the invention, a compressor vane includes a vane airfoil having an uncoated nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE A. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each Z distance in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape. X and Y distances are scalable as a function of a constant to provide a scaled-up or scaled-down airfoil.

In a further embodiment of the invention, a compressor comprises a compressor wheel having a plurality of blades cooperating with stator vanes. Each of the vanes includes an airfoil having an airfoil shape. The airfoil comprises a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE A. X and Y are distances in inches which, when connected by smooth continuing arcs, define the airfoil profile sections at each distance Z in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape.

In a yet further embodiment of the invention, a compressor comprises a compressor wheel having a plurality of blades cooperating with stator vanes, and each of the vanes include an airfoil having an uncoated nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE A. X and Y are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape. The X, Y, and Z distances are scalable as a function of a constant to provide a scaled-up or scaled-down vane airfoil.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a schematic representation of a compressor flow path through multiple stages of a gas turbine and illustrates an exemplary vane airfoil according to an embodiment of the invention; and

FIGS. 2-5 are respective perspective views of a vane according to an embodiment of the invention with the vane airfoil illustrated in conjunction with its platform and its substantially or near axial entry dovetail connection.

DETAILED DESCRIPTION OF THE INVENTION

In accordance with one embodiment of the instant invention, an article of manufacture has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE A, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.

In accordance with one embodiment of the instant invention, there is provided an airfoil compressor shape for a vane of a gas turbine that enhances the performance of the gas turbine. The airfoil shape hereof also improves the interaction between various stages of the compressor and affords improved aerodynamic efficiency, while simultaneously reducing stage airfoil thermal and mechanical stresses.

The vane airfoil profile, as embodied by the invention, is defined by a unique loci of points to achieve the necessary efficiency and loading requirements whereby improved compressor performance is obtained. These unique loci of points define the nominal airfoil profile and are identified by the X, Y, and Z Cartesian coordinates of the TABLE A that follows. The points for the coordinate values shown in TABLE A are relative to the engine centerline and for a cold, i.e., room temperature vane at various cross-sections of the vane's airfoil along its length. The positive X, Y and Z directions are axial toward the exhaust end of the turbine, tangential in the direction of engine rotation and radially outwardly toward the static case, respectively. The X, Y, and Z coordinates are given in distance dimensions, e.g., units of inches, and are joined smoothly at each Z location to form a smooth continuous airfoil cross-section. Each defined airfoil section in the X, Y plane is joined smoothly with adjacent airfoil sections in the Z direction to form the complete airfoil shape.

It will be appreciated that an airfoil heats up during use, as known by a person of ordinary skill in the art. The airfoil profile will thus change as a result of mechanical loading and temperature. Accordingly, the cold or room temperature profile, for manufacturing purposes, is given by X, Y and Z coordinates. A distance of plus or minus about 0.160 inches (+/−0.160″) from the nominal profile in a direction normal to any surface location along the nominal profile and which includes any coating, defines a profile envelope for this vane airfoil, because a manufactured vane airfoil profile may be different from the nominal airfoil profile given by the following tables. The airfoil shape is robust to this variation, without impairment of the mechanical and aerodynamic functions of the vane.

The airfoil, as embodied by the invention, can be scaled up or scaled down geometrically for introduction into similar turbine designs. Consequently, the X, Y, and Z coordinates of the nominal airfoil profile may be a function of a constant. That is, the X, Y and Z coordinate values may be multiplied or divided by the same constant or number to provide a “scaled-up” or “scaled-down” version of the vane airfoil profile, while retaining the airfoil section shape, as embodied by the invention.

Referring now to the drawings, FIG. 1 illustrates an axial compressor flow path 1 of a gas turbine compressor 2 includes a plurality of compressor stages. The compressor stages are sequentially numbered in the Figures. The compressor flow path may comprise seventeen rotor stages and stator stages. However, the exact number of rotor and stator stages is a choice of engineering design. Any number of rotor and stator stages can be provided in the combustor, as embodied by the invention. The seventeen rotor stages are merely exemplary of one turbine design. The seventeen rotor stages, as embodied by the invention, are not intended to limit the invention in any manner.

The compressor vanes impart kinetic energy to the airflow and therefore bring about a desired pressure rise. Directly following the rotor airfoils is a stage of stator airfoils. Both the rotor and stator airfoils turn the airflow, slow the airflow velocity (in the respective airfoil frame of reference), and yield a rise in the static pressure of the airflow. Typically, multiple rows of rotor/stator stages are stacked in axial flow compressors to achieve a desired discharge to inlet pressure ratio. Rotor and stator airfoils can be secured to rotor wheels or stator case by an appropriate attachment configuration, often known as a “root”, “base” or “dovetail” (see FIGS. 2-5).

A stage of the compressor 2 is exemplarily illustrated in FIG. 1. A stage of the compressor 2 comprises a plurality of circumferentially spaced blades 22 mounted on a rotor wheel 51 and a plurality of circumferentially spaced stator vanes 23 attached to a static compressor case 59, where the plurality of circumferentially spaced stator vanes 23 cooperate with the plurality of circumferentially spaced blades 22. Each of the rotor wheels is attached to aft drive shaft 58, which is connected to the turbine section of the engine. The plurality of circumferentially spaced blades 22 and plurality of circumferentially spaced stator vanes 23 lie in the flow path 1 of the compressor. The direction of airflow through the compressor flow path 1, as embodied by the invention, is indicated by the arrow 60 (FIG. 1). The stage of the compressor 2 is merely exemplarily of the stages of the compressor 2 within the scope of the invention. The stage of the compressor 2 is not intended to limit the invention in any manner.

The vanes 23, as embodied by the invention, and as illustrated in FIGS. 2-5, comprises a button 61 and a mount 62 configuration.

To define the airfoil shape of the vane airfoil, a unique set or loci of points in space are provided. This unique set or loci of points meet the stage requirements so the stage can be manufactured. This unique loci of points also meets the desired requirements for stage efficiency and reduced thermal and mechanical stresses. The loci of points are arrived at by iteration between aerodynamic and mechanical loadings enabling the compressor to run in an efficient, safe, and smooth manner.

The loci, as embodied by the invention, defines the vane airfoil profile and can comprise a set of points relative to the axis of rotation of the engine. For example, a set of points can be provided to define a vane airfoil profile. Furthermore, the vane airfoil profile, as embodied by the invention, can comprise a vanes for a Stage 1 stator vane of a compressor.

A Cartesian coordinate system of X, Y and Z values (FIG. 2) given in TABLE A below define a profile of a vane airfoil at various locations along its length. The coordinate values for the X, Y and Z coordinates are set forth in inches, although other units of dimensions may be used when the values are appropriately converted. These values exclude fillet regions of the platform. The Cartesian coordinate system has orthogonally-related X, Y and Z axes. The X axis lies parallel to the compressor rotor centerline, such as the rotary axis. A positive X coordinate value is axial toward the aft, for example the exhaust end of the compressor. A positive Y coordinate value directed aft extends tangentially in the direction of rotation of the rotor. A positive Z coordinate value is directed radially outward toward the static casing of the compressor.

TABLE A values are generated and shown to three decimal places for determining the profile of the airfoil. There are typical manufacturing tolerances as well as coatings, which should be accounted for in the actual profile of the airfoil. Accordingly, the values for the profile given are for a nominal airfoil. It will therefore be appreciated that +/− typical manufacturing tolerances, such as, +/− values, including any coating thicknesses, are additive to the X and Y values. Therefore, a distance of about +/−0.160 inches in a direction normal to any surface location along the airfoil profile defines an airfoil profile envelope for a vane airfoil design and compressor. In other words, a distance of about +/−0.160 inches in a direction normal to any surface location along the airfoil profile defines a range of variation between measured points on the actual airfoil surface at nominal cold or room temperature and the ideal position of those points, at the same temperature, as embodied by the invention. The vane airfoil design, as embodied by the invention, is robust to this range of variation without impairment of mechanical and aerodynamic functions.

The coordinate values given in the TABLE A below provide the nominal profile envelope for an exemplary S1 stage stator.

TABLE A X Y Z −2.6332 2.7242 −0.4304 −2.6458 2.7159 −0.4304 −2.6577 2.6998 −0.4304 −2.6664 2.6764 −0.4304 −2.6713 2.6469 −0.4304 −2.6731 2.6072 −0.4304 −2.6724 2.5555 −0.4304 −2.6682 2.4911 −0.4304 −2.6597 2.4134 −0.4304 −2.6461 2.3215 −0.4304 −2.6260 2.2146 −0.4304 −2.5979 2.0889 −0.4304 −2.5620 1.9450 −0.4304 −2.5165 1.7837 −0.4304 −2.4582 1.6065 −0.4304 −2.3888 1.4125 −0.4304 −2.3069 1.2023 −0.4304 −2.2138 0.9860 −0.4304 −2.1099 0.7634 −0.4304 −1.9945 0.5347 −0.4304 −1.8671 0.3009 −0.4304 −1.7281 0.0636 −0.4304 −1.5770 −0.1768 −0.4304 −1.4132 −0.4196 −0.4304 −1.2422 −0.6568 −0.4304 −1.0642 −0.8886 −0.4304 −0.8794 −1.1152 −0.4304 −0.6882 −1.3367 −0.4304 −0.4909 −1.5535 −0.4304 −0.2872 −1.7654 −0.4304 −0.0764 −1.9719 −0.4304 0.1423 −2.1699 −0.4304 0.3682 −2.3570 −0.4304 0.6005 −2.5343 −0.4304 0.8390 −2.7021 −0.4304 1.0755 −2.8553 −0.4304 1.3091 −2.9951 −0.4304 1.5395 −3.1222 −0.4304 1.7660 −3.2375 −0.4304 1.9881 −3.3416 −0.4304 2.2051 −3.4352 −0.4304 2.4156 −3.5185 −0.4304 2.6193 −3.5923 −0.4304 2.8063 −3.6543 −0.4304 2.9759 −3.7057 −0.4304 3.1278 −3.7477 −0.4304 3.2710 −3.7842 −0.4304 3.3956 −3.8136 −0.4304 3.4919 −3.8345 −0.4304 3.5691 −3.8503 −0.4304 3.6275 −3.8563 −0.4304 3.6680 −3.8373 −0.4304 3.6848 −3.8185 −0.4304 3.6926 −3.8045 −0.4304 3.6957 −3.7970 −0.4304 3.6970 −3.7932 −0.4304 3.6976 −3.7912 −0.4304 3.6981 −3.7894 −0.4304 3.6991 −3.7858 −0.4304 3.7006 −3.7785 −0.4304 3.7019 −3.7638 −0.4304 3.6999 −3.7406 −0.4304 3.6838 −3.7022 −0.4304 3.6415 −3.6671 −0.4304 3.5782 −3.6298 −0.4304 3.4994 −3.5826 −0.4304 3.3977 −3.5201 −0.4304 3.2813 −3.4464 −0.4304 3.1585 −3.3657 −0.4304 3.0221 −3.2726 −0.4304 2.8725 −3.1667 −0.4304 2.7104 −3.0470 −0.4304 2.5436 −2.9185 −0.4304 2.3722 −2.7809 −0.4304 2.1966 −2.6339 −0.4304 2.0166 −2.4776 −0.4304 1.8325 −2.3118 −0.4304 1.6444 −2.1370 −0.4304 1.4522 −1.9533 −0.4304 1.2554 −1.7613 −0.4304 1.0602 −1.5678 −0.4304 0.8659 −1.3733 −0.4304 0.6711 −1.1793 −0.4304 0.4764 −0.9854 −0.4304 0.2835 −0.7895 −0.4304 0.0932 −0.5911 −0.4304 −0.0945 −0.3901 −0.4304 −0.2795 −0.1865 −0.4304 −0.4620 0.0196 −0.4304 −0.6418 0.2281 −0.4304 −0.8188 0.4389 −0.4304 −0.9872 0.6449 −0.4304 −1.1473 0.8457 −0.4304 −1.2994 1.0412 −0.4304 −1.4440 1.2309 −0.4304 −1.5815 1.4147 −0.4304 −1.7121 1.5920 −0.4304 −1.8366 1.7626 −0.4304 −1.9497 1.9186 −0.4304 −2.0518 2.0600 −0.4304 −2.1437 2.1861 −0.4304 −2.2252 2.2970 −0.4304 −2.2966 2.3927 −0.4304 −2.3579 2.4729 −0.4304 −2.4116 2.5404 −0.4304 −2.4580 2.5961 −0.4304 −2.4978 2.6406 −0.4304 −2.5310 2.6749 −0.4304 −2.5581 2.6996 −0.4304 −2.5806 2.7154 −0.4304 −2.6016 2.7247 −0.4304 −2.6197 2.7271 −0.4304 −2.7010 2.6966 −0.0001 −2.7131 2.6881 −0.0001 −2.7241 2.6718 −0.0001 −2.7318 2.6485 −0.0001 −2.7355 2.6193 −0.0001 −2.7359 2.5803 −0.0001 −2.7334 2.5296 −0.0001 −2.7272 2.4665 −0.0001 −2.7163 2.3905 −0.0001 −2.7000 2.3007 −0.0001 −2.6769 2.1963 −0.0001 −2.6453 2.0738 −0.0001 −2.6052 1.9337 −0.0001 −2.5552 1.7769 −0.0001 −2.4919 1.6049 −0.0001 −2.4172 1.4168 −0.0001 −2.3295 1.2133 −0.0001 −2.2307 1.0041 −0.0001 −2.1209 0.7891 −0.0001 −1.9997 0.5685 −0.0001 −1.8665 0.3435 −0.0001 −1.7217 0.1155 −0.0001 −1.5648 −0.1150 −0.0001 −1.3956 −0.3475 −0.0001 −1.2194 −0.5744 −0.0001 −1.0366 −0.7959 −0.0001 −0.8475 −1.0120 −0.0001 −0.6523 −1.2232 −0.0001 −0.4513 −1.4295 −0.0001 −0.2444 −1.6310 −0.0001 −0.0305 −1.8268 −0.0001 0.1904 −2.0141 −0.0001 0.4177 −2.1909 −0.0001 0.6507 −2.3584 −0.0001 0.8894 −2.5167 −0.0001 1.1253 −2.6613 −0.0001 1.3579 −2.7931 −0.0001 1.5867 −2.9128 −0.0001 1.8112 −3.0213 −0.0001 2.0311 −3.1192 −0.0001 2.2457 −3.2072 −0.0001 2.4538 −3.2856 −0.0001 2.6548 −3.3552 −0.0001 2.8392 −3.4138 −0.0001 3.0064 −3.4623 −0.0001 3.1560 −3.5020 −0.0001 3.2970 −3.5365 −0.0001 3.4196 −3.5644 −0.0001 3.5143 −3.5844 −0.0001 3.5902 −3.5994 −0.0001 3.6476 −3.6057 −0.0001 3.6874 −3.5880 −0.0001 3.7039 −3.5701 −0.0001 3.7117 −3.5565 −0.0001 3.7147 −3.5492 −0.0001 3.7160 −3.5455 −0.0001 3.7166 −3.5436 −0.0001 3.7171 −3.5418 −0.0001 3.7180 −3.5383 −0.0001 3.7194 −3.5312 −0.0001 3.7205 −3.5168 −0.0001 3.7181 −3.4943 −0.0001 3.7013 −3.4574 −0.0001 3.6589 −3.4242 −0.0001 3.5961 −3.3881 −0.0001 3.5180 −3.3424 −0.0001 3.4169 −3.2820 −0.0001 3.3013 −3.2109 −0.0001 3.1793 −3.1329 −0.0001 3.0434 −3.0429 −0.0001 2.8942 −2.9404 −0.0001 2.7326 −2.8247 −0.0001 2.5662 −2.7006 −0.0001 2.3953 −2.5679 −0.0001 2.2200 −2.4264 −0.0001 2.0403 −2.2761 −0.0001 1.8562 −2.1169 −0.0001 1.6677 −1.9491 −0.0001 1.4745 −1.7727 −0.0001 1.2763 −1.5883 −0.0001 1.0792 −1.4026 −0.0001 0.8827 −1.2162 −0.0001 0.6857 −1.0303 −0.0001 0.4885 −0.8447 −0.0001 0.2926 −0.6576 −0.0001 0.0990 −0.4683 −0.0001 −0.0922 −0.2766 −0.0001 −0.2811 −0.0825 −0.0001 −0.4678 0.1138 −0.0001 −0.6520 0.3125 −0.0001 −0.8338 0.5136 −0.0001 −1.0070 0.7101 −0.0001 −1.1719 0.9017 −0.0001 −1.3289 1.0883 −0.0001 −1.4782 1.2695 −0.0001 −1.6202 1.4451 −0.0001 −1.7554 1.6147 −0.0001 −1.8840 1.7779 −0.0001 −2.0010 1.9273 −0.0001 −2.1067 2.0625 −0.0001 −2.2016 2.1833 −0.0001 −2.2857 2.2896 −0.0001 −2.3591 2.3812 −0.0001 −2.4222 2.4581 −0.0001 −2.4772 2.5227 −0.0001 −2.5248 2.5759 −0.0001 −2.5654 2.6184 −0.0001 −2.5991 2.6511 −0.0001 −2.6265 2.6746 −0.0001 −2.6491 2.6895 −0.0001 −2.6700 2.6980 −0.0001 −2.6879 2.6999 −0.0001 −2.8047 2.6580 0.6634 −2.8159 2.6489 0.6634 −2.8254 2.6322 0.6634 −2.8312 2.6090 0.6634 −2.8331 2.5804 0.6634 −2.8313 2.5424 0.6634 −2.8261 2.4931 0.6634 −2.8168 2.4320 0.6634 −2.8025 2.3584 0.6634 −2.7823 2.2716 0.6634 −2.7545 2.1710 0.6634 −2.7175 2.0532 0.6634 −2.6713 1.9188 0.6634 −2.6143 1.7687 0.6634 −2.5435 1.6044 0.6634 −2.4604 1.4253 0.6634 −2.3637 1.2317 0.6634 −2.2558 1.0332 0.6634 −2.1367 0.8296 0.6634 −2.0061 0.6213 0.6634 −1.8639 0.4098 0.6634 −1.7102 0.1961 0.6634 −1.5446 −0.0194 0.6634 −1.3668 −0.2365 0.6634 −1.1826 −0.4478 0.6634 −0.9925 −0.6538 0.6634 −0.7965 −0.8545 0.6634 −0.5950 −1.0502 0.6634 −0.3884 −1.2413 0.6634 −0.1764 −1.4276 0.6634 0.0423 −1.6073 0.6634 0.2664 −1.7777 0.6634 0.4957 −1.9384 0.6634 0.7297 −2.0901 0.6634 0.9682 −2.2332 0.6634 1.2030 −2.3636 0.6634 1.4334 −2.4824 0.6634 1.6591 −2.5903 0.6634 1.8797 −2.6879 0.6634 2.0950 −2.7759 0.6634 2.3044 −2.8550 0.6634 2.5077 −2.9259 0.6634 2.7047 −2.9890 0.6634 2.8856 −3.0422 0.6634 3.0494 −3.0866 0.6634 3.1958 −3.1231 0.6634 3.3337 −3.1547 0.6634 3.4537 −3.1800 0.6634 3.5462 −3.1983 0.6634 3.6203 −3.2123 0.6634 3.6762 −3.2196 0.6634 3.7157 −3.2043 0.6634 3.7324 −3.1873 0.6634 3.7402 −3.1742 0.6634 3.7431 −3.1671 0.6634 3.7444 −3.1635 0.6634 3.7449 −3.1617 0.6634 3.7454 −3.1600 0.6634 3.7463 −3.1565 0.6634 3.7476 −3.1496 0.6634 3.7485 −3.1356 0.6634 3.7455 −3.1137 0.6634 3.7271 −3.0788 0.6634 3.6839 −3.0488 0.6634 3.6220 −3.0145 0.6634 3.5450 −2.9711 0.6634 3.4454 −2.9136 0.6634 3.3313 −2.8461 0.6634 3.2105 −2.7725 0.6634 3.0758 −2.6877 0.6634 2.9280 −2.5910 0.6634 2.7674 −2.4819 0.6634 2.6017 −2.3650 0.6634 2.4310 −2.2402 0.6634 2.2553 −2.1073 0.6634 2.0748 −1.9662 0.6634 1.8894 −1.8169 0.6634 1.6991 −1.6595 0.6634 1.5038 −1.4942 0.6634 1.3031 −1.3214 0.6634 1.1033 −1.1476 0.6634 0.9038 −0.9735 0.6634 0.7040 −0.7997 0.6634 0.5037 −0.6266 0.6634 0.3035 −0.4532 0.6634 0.1052 −0.2778 0.6634 −0.0911 −0.1001 0.6634 −0.2856 0.0795 0.6634 −0.4783 0.2613 0.6634 −0.6690 0.4452 0.6634 −0.8576 0.6314 0.6634 −1.0377 0.8135 0.6634 −1.2097 0.9911 0.6634 −1.3738 1.1642 0.6634 −1.5301 1.3323 0.6634 −1.6791 1.4953 0.6634 −1.8210 1.6528 0.6634 −1.9562 1.8045 0.6634 −2.0792 1.9434 0.6634 −2.1905 2.0691 0.6634 −2.2902 2.1813 0.6634 −2.3784 2.2802 0.6634 −2.4553 2.3655 0.6634 −2.5211 2.4370 0.6634 −2.5784 2.4972 0.6634 −2.6276 2.5467 0.6634 −2.6692 2.5862 0.6634 −2.7036 2.6166 0.6634 −2.7313 2.6385 0.6634 −2.7539 2.6523 0.6634 −2.7745 2.6602 0.6634 −2.7920 2.6616 0.6634 −2.8834 2.6418 1.2102 −2.8939 2.6324 1.2102 −2.9024 2.6156 1.2102 −2.9068 2.5926 1.2102 −2.9073 2.5646 1.2102 −2.9038 2.5276 1.2102 −2.8965 2.4799 1.2102 −2.8848 2.4206 1.2102 −2.8677 2.3495 1.2102 −2.8443 2.2658 1.2102 −2.8131 2.1689 1.2102 −2.7723 2.0558 1.2102 −2.7216 1.9264 1.2102 −2.6596 1.7824 1.2102 −2.5839 1.6252 1.2102 −2.4955 1.4543 1.2102 −2.3935 1.2702 1.2102 −2.2802 1.0821 1.2102 −2.1560 0.8899 1.2102 −2.0205 0.6937 1.2102 −1.8730 0.4941 1.2102 −1.7134 0.2915 1.2102 −1.5423 0.0876 1.2102 −1.3596 −0.1168 1.2102 −1.1713 −0.3152 1.2102 −0.9780 −0.5079 1.2102 −0.7797 −0.6951 1.2102 −0.5768 −0.8771 1.2102 −0.3695 −1.0544 1.2102 −0.1579 −1.2268 1.2102 0.0595 −1.3927 1.2102 0.2838 −1.5511 1.2102 0.5150 −1.7017 1.2102 0.7524 −1.8446 1.2102 0.9941 −1.9794 1.2102 1.2318 −2.1020 1.2102 1.4649 −2.2135 1.2102 1.6930 −2.3145 1.2102 1.9151 −2.4055 1.2102 2.1310 −2.4874 1.2102 2.3402 −2.5608 1.2102 2.5423 −2.6264 1.2102 2.7370 −2.6847 1.2102 2.9152 −2.7338 1.2102 3.0764 −2.7748 1.2102 3.2203 −2.8087 1.2102 3.3558 −2.8380 1.2102 3.4736 −2.8616 1.2102 3.5644 −2.8788 1.2102 3.6372 −2.8919 1.2102 3.6919 −2.8999 1.2102 3.7315 −2.8865 1.2102 3.7484 −2.8702 1.2102 3.7562 −2.8574 1.2102 3.7592 −2.8504 1.2102 3.7604 −2.8468 1.2102 3.7610 −2.8450 1.2102 3.7615 −2.8433 1.2102 3.7623 −2.8399 1.2102 3.7635 −2.8331 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1.5442 15.4290 −1.7491 1.6459 15.4290 −1.8544 1.7373 15.4290 −1.9491 1.8186 15.4290 −2.0330 1.8899 15.4290 −2.1062 1.9512 15.4290 −2.1686 2.0025 15.4290 −2.2224 2.0456 15.4290 −2.2682 2.0813 15.4290 −2.3062 2.1101 15.4290 −2.3372 2.1324 15.4290 −2.3618 2.1485 15.4290 −2.3808 2.1596 15.4290 −2.3974 2.1674 15.4290 −2.4115 2.1712 15.4290 −2.3684 2.1817 15.9759 −2.3723 2.1713 15.9759 −2.3701 2.1564 15.9759 −2.3636 2.1389 15.9759 −2.3537 2.1188 15.9759 −2.3386 2.0932 15.9759 −2.3172 2.0610 15.9759 −2.2888 2.0218 15.9759 −2.2530 1.9752 15.9759 −2.2096 1.9203 15.9759 −2.1579 1.8568 15.9759 −2.0961 1.7824 15.9759 −2.0241 1.6970 15.9759 −1.9423 1.6005 15.9759 −1.8505 1.4930 15.9759 −1.7481 1.3750 15.9759 −1.6351 1.2465 15.9759 −1.5164 1.1132 15.9759 −1.3915 0.9754 15.9759 −1.2602 0.8335 15.9759 −1.1223 0.6876 15.9759 −0.9775 0.5378 15.9759 −0.8257 0.3845 15.9759 −0.6664 0.2280 15.9759 −0.5049 0.0741 15.9759 −0.3412 −0.0767 15.9759 −0.1751 −0.2240 15.9759 −0.0061 −0.3674 15.9759 0.1660 −0.5063 15.9759 0.3416 −0.6402 15.9759 0.5217 −0.7679 15.9759 0.7065 −0.8888 15.9759 0.8961 −1.0031 15.9759 1.0896 −1.1118 15.9759 1.2863 −1.2160 15.9759 1.4794 −1.3126 15.9759 1.6682 −1.4024 15.9759 1.8517 −1.4859 15.9759 2.0298 −1.5633 15.9759 2.2021 −1.6353 15.9759 2.3684 −1.7021 15.9759 2.5286 −1.7643 15.9759 2.6824 −1.8222 15.9759 2.8227 −1.8736 15.9759 2.9493 −1.9189 15.9759 3.0621 −1.9584 15.9759 3.1680 −1.9950 15.9759 3.2599 −2.0263 15.9759 3.3307 −2.0502 15.9759 3.3874 −2.0692 15.9759 3.4299 −2.0834 15.9759 3.4619 −2.0936 15.9759 3.4802 −2.0907 15.9759 3.4895 −2.0830 15.9759 3.4927 −2.0779 15.9759 3.4939 −2.0751 15.9759 3.4944 −2.0737 15.9759 3.4948 −2.0722 15.9759 3.4954 −2.0693 15.9759 3.4958 −2.0635 15.9759 3.4934 −2.0520 15.9759 3.4824 −2.0375 15.9759 3.4527 −2.0234 15.9759 3.4125 −2.0058 15.9759 3.3590 −1.9822 15.9759 3.2921 −1.9527 15.9759 3.2053 −1.9140 15.9759 3.1053 −1.8689 15.9759 2.9989 −1.8204 15.9759 2.8795 −1.7650 15.9759 2.7473 −1.7025 15.9759 2.6025 −1.6324 15.9759 2.4519 −1.5576 15.9759 2.2958 −1.4777 15.9759 2.1344 −1.3924 15.9759 1.9679 −1.3012 15.9759 1.7966 −1.2037 15.9759 1.6207 −1.0997 15.9759 1.4402 −0.9888 15.9759 1.2554 −0.8708 15.9759 1.0727 −0.7494 15.9759 0.8925 −0.6247 15.9759 0.7146 −0.4970 15.9759 0.5390 −0.3663 15.9759 0.3659 −0.2322 15.9759 0.1957 −0.0942 15.9759 0.0281 0.0471 15.9759 −0.1372 0.1913 15.9759 −0.3008 0.3375 15.9759 −0.4630 0.4851 15.9759 −0.6242 0.6339 15.9759 −0.7794 0.7784 15.9759 −0.9287 0.9184 15.9759 −1.0725 1.0537 15.9759 −1.2107 1.1842 15.9759 −1.3437 1.3097 15.9759 −1.4715 1.4299 15.9759 −1.5944 1.5448 15.9759 −1.7071 1.6490 15.9759 −1.8100 1.7424 15.9759 −1.9026 1.8253 15.9759 −1.9847 1.8979 15.9759 −2.0565 1.9602 15.9759 −2.1179 2.0123 15.9759 −2.1710 2.0559 15.9759 −2.2162 2.0918 15.9759 −2.2539 2.1208 15.9759 −2.2847 2.1432 15.9759 −2.3089 2.1595 15.9759 −2.3277 2.1708 15.9759 −2.3440 2.1790 15.9759 −2.3579 2.1835 15.9759 −2.2903 2.2479 16.5227 −2.2944 2.2376 16.5227 −2.2924 2.2227 16.5227 −2.2863 2.2050 16.5227 −2.2767 2.1847 16.5227 −2.2623 2.1586 16.5227 −2.2417 2.1257 16.5227 −2.2144 2.0855 16.5227 −2.1799 2.0376 16.5227 −2.1381 1.9812 16.5227 −2.0884 1.9158 16.5227 −2.0290 1.8390 16.5227 −1.9599 1.7508 16.5227 −1.8816 1.6509 16.5227 −1.7937 1.5395 16.5227 −1.6957 1.4170 16.5227 −1.5878 1.2834 16.5227 −1.4745 1.1446 16.5227 −1.3553 1.0009 16.5227 −1.2301 0.8526 16.5227 −1.0985 0.6999 16.5227 −0.9603 0.5430 16.5227 −0.8152 0.3821 16.5227 −0.6628 0.2178 16.5227 −0.5079 0.0562 16.5227 −0.3499 −0.1022 16.5227 −0.1884 −0.2570 16.5227 −0.0229 −0.4077 16.5227 0.1472 −0.5537 16.5227 0.3219 −0.6942 16.5227 0.5009 −0.8273 16.5227 0.6844 −0.9526 16.5227 0.8720 −1.0706 16.5227 1.0628 −1.1829 16.5227 1.2564 −1.2903 16.5227 1.4462 −1.3895 16.5227 1.6317 −1.4814 16.5227 1.8125 −1.5665 16.5227 1.9883 −1.6454 16.5227 2.1589 −1.7187 16.5227 2.3239 −1.7866 16.5227 2.4829 −1.8496 16.5227 2.6357 −1.9081 16.5227 2.7752 −1.9597 16.5227 2.9011 −2.0051 16.5227 3.0134 −2.0446 16.5227 3.1188 −2.0809 16.5227 3.2104 −2.1119 16.5227 3.2810 −2.1354 16.5227 3.3375 −2.1540 16.5227 3.3799 −2.1679 16.5227 3.4118 −2.1779 16.5227 3.4300 −2.1751 16.5227 3.4393 −2.1676 16.5227 3.4425 −2.1625 16.5227 3.4437 −2.1597 16.5227 3.4442 −2.1583 16.5227 3.4445 −2.1569 16.5227 3.4451 −2.1540 16.5227 3.4454 −2.1481 16.5227 3.4426 −2.1366 16.5227 3.4310 −2.1224 16.5227 3.4011 −2.1087 16.5227 3.3607 −2.0914 16.5227 3.3069 −2.0682 16.5227 3.2397 −2.0390 16.5227 3.1525 −2.0008 16.5227 3.0521 −1.9561 16.5227 2.9454 −1.9077 16.5227 2.8258 −1.8524 16.5227 2.6934 −1.7897 16.5227 2.5485 −1.7192 16.5227 2.3981 −1.6438 16.5227 2.2424 −1.5631 16.5227 2.0818 −1.4768 16.5227 1.9164 −1.3844 16.5227 1.7466 −1.2854 16.5227 1.5725 −1.1795 16.5227 1.3945 −1.0665 16.5227 1.2126 −0.9459 16.5227 1.0333 −0.8215 16.5227 0.8565 −0.6931 16.5227 0.6819 −0.5613 16.5227 0.5097 −0.4259 16.5227 0.3402 −0.2861 16.5227 0.1742 −0.1419 16.5227 0.0119 0.0062 16.5227 −0.1474 0.1573 16.5227 −0.3044 0.3108 16.5227 −0.4598 0.4660 16.5227 −0.6140 0.6223 16.5227 −0.7624 0.7742 16.5227 −0.9052 0.9212 16.5227 −1.0427 1.0633 16.5227 −1.1751 1.2001 16.5227 −1.3025 1.3315 16.5227 −1.4250 1.4575 16.5227 −1.5429 1.5778 16.5227 −1.6512 1.6869 16.5227 −1.7500 1.7848 16.5227 −1.8391 1.8717 16.5227 −1.9183 1.9478 16.5227 −1.9875 2.0132 16.5227 −2.0468 2.0677 16.5227 −2.0982 2.1135 16.5227 −2.1419 2.1514 16.5227 −2.1784 2.1819 16.5227 −2.2082 2.2056 16.5227 −2.2318 2.2230 16.5227 −2.2501 2.2351 16.5227 −2.2661 2.2440 16.5227 −2.2798 2.2492 16.5227 −2.2010 2.3386 17.0696 −2.2054 2.3284 17.0696 −2.2039 2.3134 17.0696 −2.1984 2.2955 17.0696 −2.1897 2.2748 17.0696 −2.1764 2.2481 17.0696 −2.1572 2.2142 17.0696 −2.1317 2.1729 17.0696 −2.0994 2.1234 17.0696 −2.0602 2.0651 17.0696 −2.0137 1.9972 17.0696 −1.9581 1.9176 17.0696 −1.8934 1.8259 17.0696 −1.8199 1.7222 17.0696 −1.7374 1.6066 17.0696 −1.6455 1.4794 17.0696 −1.5442 1.3405 17.0696 −1.4378 1.1960 17.0696 −1.3260 1.0463 17.0696 −1.2084 0.8915 17.0696 −1.0849 0.7319 17.0696 −0.9550 0.5677 17.0696 −0.8185 0.3994 17.0696 −0.6750 0.2277 17.0696 −0.5287 0.0592 17.0696 −0.3791 −0.1055 17.0696 −0.2257 −0.2658 17.0696 −0.0681 −0.4213 17.0696 0.0941 −0.5715 17.0696 0.2614 −0.7160 17.0696 0.4343 −0.8539 17.0696 0.6133 −0.9849 17.0696 0.7982 −1.1091 17.0696 0.9880 −1.2277 17.0696 1.1820 −1.3414 17.0696 1.3735 −1.4466 17.0696 1.5607 −1.5436 17.0696 1.7432 −1.6332 17.0696 1.9208 −1.7160 17.0696 2.0930 −1.7925 17.0696 2.2594 −1.8632 17.0696 2.4200 −1.9284 17.0696 2.5745 −1.9887 17.0696 2.7155 −2.0417 17.0696 2.8431 −2.0881 17.0696 2.9568 −2.1282 17.0696 3.0637 −2.1649 17.0696 3.1566 −2.1960 17.0696 3.2282 −2.2196 17.0696 3.2856 −2.2382 17.0696 3.3286 −2.2520 17.0696 3.3610 −2.2620 17.0696 3.3796 −2.2597 17.0696 3.3891 −2.2523 17.0696 3.3923 −2.2472 17.0696 3.3935 −2.2444 17.0696 3.3939 −2.2429 17.0696 3.3943 −2.2415 17.0696 3.3948 −2.2385 17.0696 3.3949 −2.2326 17.0696 3.3917 −2.2212 17.0696 3.3796 −2.2074 17.0696 3.3494 −2.1940 17.0696 3.3087 −2.1770 17.0696 3.2544 −2.1541 17.0696 3.1868 −2.1254 17.0696 3.0990 −2.0875 17.0696 2.9980 −2.0431 17.0696 2.8907 −1.9948 17.0696 2.7706 −1.9394 17.0696 2.6377 −1.8763 17.0696 2.4925 −1.8051 17.0696 2.3420 −1.7288 17.0696 2.1864 −1.6468 17.0696 2.0259 −1.5589 17.0696 1.8609 −1.4645 17.0696 1.6917 −1.3632 17.0696 1.5184 −1.2546 17.0696 1.3413 −1.1383 17.0696 1.1607 −1.0141 17.0696 0.9829 −0.8855 17.0696 0.8079 −0.7524 17.0696 0.6355 −0.6154 17.0696 0.4658 −0.4742 17.0696 0.3003 −0.3288 17.0696 0.1395 −0.1787 17.0696 −0.0167 −0.0243 17.0696 −0.1692 0.1339 17.0696 −0.3187 0.2949 17.0696 −0.4661 0.4580 17.0696 −0.6120 0.6224 17.0696 −0.7523 0.7822 17.0696 −0.8873 0.9369 17.0696 −1.0173 1.0862 17.0696 −1.1425 1.2300 17.0696 −1.2631 1.3681 17.0696 −1.3792 1.5003 17.0696 −1.4909 1.6267 17.0696 −1.5935 1.7415 17.0696 −1.6872 1.8446 17.0696 −1.7717 1.9363 17.0696 −1.8467 2.0167 17.0696 −1.9123 2.0859 17.0696 −1.9685 2.1437 17.0696 −2.0172 2.1926 17.0696 −2.0586 2.2330 17.0696 −2.0932 2.2658 17.0696 −2.1215 2.2914 17.0696 −2.1439 2.3102 17.0696 −2.1615 2.3235 17.0696 −2.1770 2.3333 17.0696 −2.1904 2.3392 17.0696 −2.1188 2.4229 17.5696 −2.1235 2.4128 17.5696 −2.1224 2.3978 17.5696 −2.1175 2.3796 17.5696 −2.1095 2.3586 17.5696 −2.0971 2.3313 17.5696 −2.0793 2.2967 17.5696 −2.0553 2.2543 17.5696 −2.0250 2.2034 17.5696 −1.9882 2.1434 17.5696 −1.9445 2.0735 17.5696 −1.8923 1.9913 17.5696 −1.8316 1.8966 17.5696 −1.7627 1.7895 17.5696 −1.6853 1.6700 17.5696 −1.5990 1.5384 17.5696 −1.5040 1.3947 17.5696 −1.4044 1.2450 17.5696 −1.2996 1.0898 17.5696 −1.1893 0.9292 17.5696 −1.0734 0.7634 17.5696 −0.9513 0.5927 17.5696 −0.8226 0.4177 17.5696 −0.6868 0.2393 17.5696 −0.5476 0.0642 17.5696 −0.4045 −0.1072 17.5696 −0.2568 −0.2742 17.5696 −0.1041 −0.4363 17.5696 0.0541 −0.5932 17.5696 0.2181 −0.7444 17.5696 0.3889 −0.8891 17.5696 0.5670 −1.0269 17.5696 0.7521 −1.1577 17.5696 0.9419 −1.2818 17.5696 1.1353 −1.3998 17.5696 1.3256 −1.5083 17.5696 1.5120 −1.6084 17.5696 1.6942 −1.7009 17.5696 1.8714 −1.7860 17.5696 2.0433 −1.8646 17.5696 2.2098 −1.9370 17.5696 2.3705 −2.0037 17.5696 2.5252 −2.0651 17.5696 2.6666 −2.1189 17.5696 2.7945 −2.1656 17.5696 2.9087 −2.2059 17.5696 3.0160 −2.2426 17.5696 3.1094 −2.2736 17.5696 3.1814 −2.2970 17.5696 3.2390 −2.3154 17.5696 3.2823 −2.3290 17.5696 3.3149 −2.3389 17.5696 3.3335 −2.3370 17.5696 3.3432 −2.3297 17.5696 3.3464 −2.3246 17.5696 3.3476 −2.3217 17.5696 3.3480 −2.3203 17.5696 3.3484 −2.3188 17.5696 3.3488 −2.3159 17.5696 3.3488 −2.3099 17.5696 3.3452 −2.2986 17.5696 3.3326 −2.2851 17.5696 3.3021 −2.2720 17.5696 3.2610 −2.2552 17.5696 3.2064 −2.2327 17.5696 3.1383 −2.2043 17.5696 3.0500 −2.1668 17.5696 2.9485 −2.1226 17.5696 2.8407 −2.0745 17.5696 2.7200 −2.0190 17.5696 2.5868 −1.9556 17.5696 2.4413 −1.8838 17.5696 2.2903 −1.8063 17.5696 2.1341 −1.7228 17.5696 1.9734 −1.6330 17.5696 1.8086 −1.5366 17.5696 1.6401 −1.4332 17.5696 1.4681 −1.3224 17.5696 1.2930 −1.2039 17.5696 1.1150 −1.0773 17.5696 0.9403 −0.9464 17.5696 0.7692 −0.8110 17.5696 0.6013 −0.6716 17.5696 0.4367 −0.5279 17.5696 0.2759 −0.3793 17.5696 0.1196 −0.2252 17.5696 −0.0324 −0.0656 17.5696 −0.1806 0.0989 17.5696 −0.3253 0.2674 17.5696 −0.4670 0.4383 17.5696 −0.6064 0.6111 17.5696 −0.7396 0.7793 17.5696 −0.8674 0.9424 17.5696 −0.9902 1.0999 17.5696 −1.1085 1.2517 17.5696 −1.2225 1.3974 17.5696 −1.3324 1.5369 17.5696 −1.4384 1.6701 17.5696 −1.5359 1.7910 17.5696 −1.6252 1.8997 17.5696 −1.7057 1.9963 17.5696 −1.7773 2.0811 17.5696 −1.8400 2.1540 17.5696 −1.8939 2.2151 17.5696 −1.9406 2.2666 17.5696 −1.9804 2.3094 17.5696 −2.0137 2.3441 17.5696 −2.0409 2.3713 17.5696 −2.0627 2.3914 17.5696 −2.0798 2.4056 17.5696 −2.0949 2.4162 17.5696 −2.1080 2.4229 17.5696

In the exemplary embodiments, as embodied by the invention, for example the stage compressor vane, there are many airfoils, which are un-cooled. For reference purposes only, there is established point-0 passing through the intersection of the airfoil and the platform along the stacking axis.

It will also be appreciated that the exemplary airfoil(s) disclosed in the above TABLE A may be scaled up or down geometrically for use in other similar compressor designs. Consequently, the coordinate values set forth in TABLE A may be scaled upwardly or downwardly such TABLE A the airfoil profile shape remains unchanged. A scaled version of the coordinates in the TABLE A would be represented by X, Y and Z coordinates values of the TABLE A multiplied or divided by a constant.

In particular, as embodied by the invention, the airfoil as defined by TABLE A, can be applied in a compressor of a turbine, for example, but not limited to, as General Electric “7FA+e” or “7FA.05” compressor. Moreover, the vane airfoil profile, as embodied by the invention, can comprise a stage 1 stator vane of such a compressor. This compressor is merely illustrative of the intended applications for the airfoil, as embodied by the invention. Moreover, it is envisioned that the airfoil of TABLE A, as embodied by the invention, can also be used as stator vanes in compressors for example for GE Frame F-class turbines, as well as GE's Frame 6 and 9 turbines, given the scaling of the airfoil, as embodied by the invention.

The airfoils impart kinetic energy to the airflow and therefore bring about a desired flow across the compressor. The airfoils turn the fluid flow, slow the fluid flow velocity (in the respective airfoil frame of reference), and yield a rise in the static pressure of the fluid flow. The configuration of the airfoil (along with its interaction with surrounding airfoils), as embodied by the invention, including its peripheral surface provides for stage airflow efficiency, enhanced aeromechanics, smooth laminar flow from stage to stage, reduced thermal stresses, enhanced interrelation of the stages to effectively pass the airflow from stage to stage, and reduced mechanical stresses, among other desirable aspects of the invention. Typically, multiple rows of airfoil stages, such as, but not limited to, rotor/stator airfoils, are stacked to achieve a desired discharge to inlet pressure ratio. Airfoils can be secured to wheels or a case by an appropriate attachment configuration, often known as a “root”, “base” or “dovetail”.

The configuration of the airfoil and any interaction with surrounding airfoils, as embodied by the invention, that provide the desirable aspects fluid flow dynamics and laminar flow of the invention can be determined by various means. Fluid flow from a preceding/upstream airfoil intersects with the airfoil, as embodied by the invention, and via the configuration of the instant airfoil, flow over and around the airfoil, as embodied by the invention, is enhanced. In particular, the fluid dynamics and laminar flow from the airfoil, as embodied by the invention, is enhanced. There is a smooth transition fluid flow from any preceding/upstream airfoil(s) and a smooth transition fluid flow to the adjacent/downstream airfoil(s). Moreover, the flow from the airfoil, as embodied by the invention, proceeds to the adjacent/downstream airfoil(s) is enhanced due to the enhanced laminar fluid flow off of the airfoil, as embodied by the invention. Therefore, the configuration of the airfoil, as embodied by the invention, assists in the prevention of turbulent fluid flow in the unit comprising the airfoil, as embodied by the invention.

For example, but in no way limiting of the invention, the airfoil configuration (with or without fluid flow interaction) can be determined by computational modeling, Fluid Dynamics (CFD); traditional fluid dynamics analysis; Euler and Navier-Stokes equations; for transfer functions, algorithms, manufacturing: manual positioning, flow testing (for example in wind tunnels), and modification of the airfoil; in-situ testing; modeling: application of scientific principles to design or develop the airfoils, machines, apparatus, or manufacturing processes; airfoil flow testing and modification; combinations thereof, and other design processes and practices. These methods of determination are merely exemplary, and are not intended to limit the invention in any manner.

As noted above, the airfoil configuration (along with its interaction with surrounding airfoils), as embodied by the invention, including its peripheral surface provides for stage airflow efficiency, enhanced aeromechanics, smooth laminar flow from stage to stage, reduced thermal stresses, enhanced interrelation of the stages to effectively pass the airflow from stage to stage, and reduced mechanical stresses, among other desirable aspects of the invention, compared to other similar airfoils, which have like applications. Of course, other such advantages are within the scope of the invention.

While various embodiments are described herein, it will be appreciated from the specification that various combinations of elements, variations, or improvements therein may be made by those skilled in the art, and are within the scope of the invention. 

What is claimed is:
 1. An article of manufacture, the article having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE A, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.
 2. An article of manufacture according to claim 1, wherein the airfoil shape comprises an airfoil.
 3. An article of manufacture according to claim 2, wherein said airfoil shape lies in an envelope within ±0.160 inches in a direction normal to any article surface location.
 4. An article of manufacture according to claim 1, wherein the airfoil shape comprises a stator vane.
 5. A compressor comprising a compressor wheel having a plurality of blades, each of said blades cooperating with a plurality of stator vanes, the plurality of stator vanes comprising an airfoil having an airfoil shape, said airfoil shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE A, wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define the airfoil profile sections at each distance Z in inches, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.
 6. A compressor comprising a compressor wheel having a plurality of blades, each of said blades cooperating with a plurality of stator vanes, the plurality of stator vanes comprising an airfoil having an uncoated nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE A, wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape, the X and Y distances being scalable as a function of the same constant or number to provide at least one of a scaled up vane airfoil and scaled down vane airfoil.
 7. A compressor according to claim 6 wherein the plurality of stator vanes comprise a Stage 1 stator vane.
 8. A compressor according to claim 6 wherein said airfoil shape lies in an envelope within ±0.160 inches in a direction normal to any airfoil surface location. 